CubeSat Lunar Positioning System Enabled by Novel On-Board Electric Propulsion

Abstract

Due to the advances in miniaturization, CubeSats are becoming more versatile, with projected mission capabilities that are traditionally reserved for larger satellites. However, they are still limited by a lack of efficient propulsive means. A novel electric thruster based on electron cyclotron resonance heating and magnetic nozzle acceleration may provide a suitable yet simple solution. This device, while currently providing 1000 s I sp and 1 mN of thrust at 30 W of power, may enable lunar CubeSat missions from geosynchronous earth orbit using on-board propulsion. An example mission to provide GPS on the lunar surface using 3-U CubeSats in a 60°:28/4/6 Walker constellation with a semimajor axis of 4000 km is proposed; a preliminary assessment of this mission, together with the satellite architecture and cost, is performed. Concurrent trajectory design for very-low-energy transfers is used to demonstrate the feasibility of the mission and its impact on the spacecraft design.